Full-annular combustion chamber testing device
By designing a full-annular combustion chamber test device, using components such as micro turbojet engines and annular drainage channels, comprehensive and accurate testing of the performance of the full-annular combustion chamber is achieved, and the problems of difficult testing and inaccurate data in the existing technology are solved.
Patent Information
- Application Number
- CN202421998441.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-08-16
- Publication Date
- 2025-06-03
- Estimated Expiration
- 2034-08-16
AI Technical Summary
In the design process of the full-ring combustion chamber of a micro-aero engine, there is a lack of test verification methods and the computer simulation results cannot be checked, resulting in incomplete and inaccurate test data.
A fully annular combustion chamber test device is designed, including a diversion pipe section, a drainage pipe section, an inlet pipe section, a test pipe section, an outlet pipe section and an exhaust pipe section, and is equipped with a micro turbojet engine, annular drainage passage, a tapered pipe, a cap cover, a measuring device and an explosion-proof transparent window.
Through this device, performance indicators such as mass flow rate, total pressure recovery coefficient, outlet temperature field distribution, combustion efficiency and pollutant emissions of the full annular combustion chamber can be accurately measured, solving the problems of incomplete and inaccurate test data.
Smart Images
Figure CN222938752U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of combustion chamber tests, and particularly relates to a full-annular combustion chamber test device. Background Art
[0002] In the design process of the full-annular combustion chamber of a micro-aero engine, due to the lack of test verification means, the computer simulation results cannot be checked. Only the designed full-annular combustion chamber can be assembled into the whole engine for hot commissioning to obtain data, and only some overall performance data of the full-annular combustion chamber can be obtained. Since the sizes of the components of the micro-aero engine are small, the influence of the measurement components of the full-annular combustion chamber after being placed into the whole engine is large, and the deviation between the measured data and the true state of the combustion chamber is difficult to estimate. Therefore, there is an urgent need for a special test device to test the performance of the full-annular combustion chamber. Content of the Utility Model
[0003] Aiming at the above deficiencies of the prior art, the utility model provides a full-annular combustion chamber test device, which solves the problems of great difficulty in testing the full-annular combustion chamber and incomplete and inaccurate test data.
[0004] To achieve the above object, the technical solution adopted by the utility model is as follows:
[0005] Provide a full-annular combustion chamber test device, which includes a flow guide pipe section, a drainage pipe section, an inlet pipe section, a test pipe section, an outlet pipe section and an exhaust pipe section connected in sequence. The flow guide pipe section cooperates with a gas supply device. An annular drainage channel communicated with its interior is arranged on the circumferential direction of the drainage pipe section. Measuring devices for measuring test parameters are arranged in both the inlet pipe section and the outlet pipe section. A full-annular combustion chamber is arranged in the test pipe section. An inlet hood for facilitating the acceleration and pressurization of the air flow is arranged at the rear port of the inlet pipe section, and an outlet hood for facilitating the deceleration and pressure expansion of the air flow is arranged at the front port of the outlet pipe section.
[0006] Further, both the inlet pipe section and the outlet pipe section are tapered pipes. The large-diameter end and the small-diameter end of the inlet pipe section are smoothly connected to the drainage pipe section and the test pipe section respectively. The small-diameter end and the large-diameter end of the outlet pipe section are smoothly connected to the test pipe section and the exhaust pipe section respectively.
[0007] Further, both the inlet hood and the outlet hood are fixedly connected to the inner peripheral walls of the inlet pipe section and the outlet pipe section respectively through a plurality of support columns. Both the inlet hood and the outlet hood are conical, and the cone tips of the inlet hood and the outlet hood point to the large-diameter ends of the inlet pipe section and the outlet pipe section respectively.
[0008] Further, a fuel main pipe is arranged on the inlet pipe section. The interior of the support column connected to the inlet hood is hollow. The fuel main pipe is led to the inside of the inlet hood through the inner cavity of the support column and is connected to a plurality of fuel small pipes in the full-annular combustion chamber through a fuel transfer disk.
[0009] Furthermore, the measuring device includes a flue gas analyzer, a carbon emission detector, and several total temperature and total pressure sensors, and the several total temperature and total pressure sensors are evenly arranged in the circumferential direction at the front ports of the inlet pipe section and the outlet pipe section.
[0010] Furthermore, the included angle between the air flow direction of the annular drainage channel and the air flow direction inside the drainage pipe section is an acute angle.
[0011] Furthermore, a rectifying honeycomb plate is arranged inside the drainage pipe section, and the rectifying honeycomb plate is located at the rear end of the annular drainage channel.
[0012] Furthermore, the air supply device is a micro turbojet engine, and there is a certain distance between the exhaust port of the micro turbojet engine and the front port of the diversion pipe section.
[0013] Furthermore, an explosion-proof and high-temperature-resistant transparent window is arranged on the side wall of the test pipe section.
[0014] The beneficial effects of the utility model are as follows:
[0015] 1. In this solution, the air flow at the outlet of the micro turbojet engine and the air flow drawn from the subsequent annular drainage channel are used as the oncoming flow, which can meet the air mass flow required for the full annular combustion chamber test; by adjusting the rotational speed of the micro turbojet engine, the air flow rate at the inlet of the full annular combustion chamber can be adjusted, avoiding the construction of a complex air supply and control system to control the test cost.
[0016] 2. In this solution, through the cooperation of the inlet pipe section and the inlet cap, the acceleration and pressurization at the front end of the full annular combustion chamber are realized, and through the cooperation of the outlet pipe section and the outlet cap, the deceleration and pressure expansion at the rear end of the full annular combustion chamber are realized; total temperature and total pressure sensors are distributed circumferentially at the front and rear of the full annular combustion chamber, and measuring devices such as a flue gas analyzer and a carbon emission detector can also be installed. Through the explosion-proof and high-temperature-resistant transparent window, information such as the internal temperature field distribution of the full annular combustion chamber can be monitored or thermally radiated, so as to obtain various performance indicators of the full annular combustion chamber, such as the mass flow rate, total pressure recovery coefficient, outlet temperature field distribution, combustion efficiency, and pollutant emissions. The test data is accurate and comprehensive. Description of the Drawings
[0017] Figure 1 It is a structural schematic diagram of the full annular combustion chamber test device.
[0018] Figure 2 It is a sectional view of the full annular combustion chamber test device.
[0019] Among them, 1 is the diversion pipe section, 2 is the drainage pipe section, 3 is the inlet pipe section, 4 is the test pipe section, 5 is the outlet pipe section, 6 is the exhaust pipe section, 7 is the annular drainage channel, 8 is the full annular combustion chamber, 9 is the inlet hood, 10 is the outlet hood, 11 is the support column, 12 is the fuel manifold, 13 is the fuel transfer plate, 14 is the fuel small pipe, 15 is the total temperature and total pressure sensor, 16 is the rectifying honeycomb plate, 17 is the micro turbojet engine, 18 is the explosion-proof and high-temperature resistant transparent window, and 19 is the igniter. Specific Embodiment
[0020] The specific embodiments of the present invention will be described below to facilitate those skilled in the art of the present technology to understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific embodiments. For those of ordinary skill in the art of the present technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the appended claims, these changes are obvious, and all utility models created using the concept of the present invention are within the scope of protection.
[0021] As Figure 1 and Figure 2 shown, the full annular combustion chamber test device of this solution includes a diversion pipe section 1, a drainage pipe section 2, an inlet pipe section 3, a test pipe section 4, an outlet pipe section 5, and an exhaust pipe section 6 connected in sequence. The diversion pipe section 1 cooperates with the air supply device. Preferably, the air supply device is a micro turbojet engine 17, and there is a certain distance between the exhaust port of the micro turbojet engine 17 and the front port of the diversion pipe section 1 to obtain a larger air intake volume; an annular drainage channel 7 communicating with its interior is provided in the circumferential direction of the drainage pipe section 2, and the included angle between the air flow direction of the annular drainage channel 7 and the air flow direction inside the drainage pipe section 2 is an acute angle; this solution uses the air flow at the outlet of the micro turbojet engine 17 and the induced air flow in the subsequent annular drainage channel 7 as the oncoming flow, which can meet the air mass flow required for the test of the full annular combustion chamber 8; by adjusting the rotation speed of the micro turbojet engine 17, the air flow volume at the inlet of the full annular combustion chamber 8 can be adjusted, avoiding the construction of a complex air supply and control system to control the test cost; a rectifying honeycomb plate 16 is provided inside the drainage pipe section 2, and the rectifying honeycomb plate 16 is located at the rear end of the annular drainage channel 7 to improve the air flow quality.
[0022] The test section 4 of this solution is internally provided with a full-annular combustor 8. The inlet section 3 and the outlet section 5 are both tapered pipes. The large-diameter end and the small-diameter end of the inlet section 3 are smoothly connected to the diversion section 2 and the test section 4 respectively. The small-diameter end and the large-diameter end of the outlet section 5 are smoothly connected to the test section 4 and the exhaust pipe section 6 respectively. An inlet cap 9 is provided at the rear port of the inlet section 3, and an outlet cap 10 is provided at the front port of the outlet section 5. Both the inlet cap 9 and the outlet cap 10 are fixedly connected to the inner peripheral walls of the inlet section 3 and the outlet section 5 respectively through a number of support columns 11. Both the inlet cap 9 and the outlet cap 10 are conical, and the tips of the inlet cap 9 and the outlet cap 10 point to the large-diameter ends of the inlet section 3 and the outlet section 5 respectively. Through the cooperation of the inlet section 3 and the inlet cap 9, this solution realizes the speed increase and pressure boost at the front end of the full-annular combustor 8. Through the cooperation of the outlet section 5 and the outlet cap 10, it realizes the speed reduction and pressure expansion at the rear end of the full-annular combustor 8, so as to meet the parameter requirements for the test of the full-annular combustor 8.
[0023] A fuel main pipe 12 is provided on the inlet section 3. The support column 11 connected to the inlet cap 9 is hollow inside. The fuel main pipe 12 is led into the inlet cap 9 through the inner cavity of the support column 11 and is connected to a number of fuel small pipes 14 inside the full-annular combustor 8 through a fuel transfer plate 13. This solution can supply fuel to the full-annular combustor 8 through the fuel main pipe 12. An igniter 19 is provided inside the full-annular combustor 8 to realize the ignition of the fuel.
[0024] Measuring devices for measuring test parameters are provided inside both the inlet section 3 and the outlet section 5. The measuring devices include a flue gas analyzer, a carbon emission detector, and a number of total temperature and total pressure sensors 15. The number of total temperature and total pressure sensors 15 are evenly arranged in the circumferential direction at the front ports of the inlet section 3 and the outlet section 5, so as to obtain various performance indicators such as the mass flow rate, total pressure recovery coefficient, outlet temperature field distribution, combustion efficiency, and pollutant emissions of the full-annular combustor 8. An explosion-proof and high-temperature-resistant transparent window 18 is provided on the side wall of the test section 4, which can monitor or detect information such as the internal temperature field distribution of the full-annular combustor 8 by thermal radiation, and the test data is accurate and comprehensive.
[0025] The test process of this solution is specifically described below:
[0026] After the micro turbojet engine 17 operates, the exhaust gas enters the diversion pipe section 1 through its own exhaust nozzle, achieving the first diversion; the annular diversion channel 7 on the diversion pipe section 2 can introduce the ambient low-temperature air into the pipe for the second time, achieving the second diversion; the high-temperature gas discharged by the micro turbojet engine 17 and the low-temperature air diverted for the first and second times are rectified and mixed through the rectifying honeycomb plate 16; and then flows out with relatively stable air flow quality, and then enters the front inlet of the full annular combustor 8 after being accelerated by the inlet cap 9. The air and fuel entering the test pipe section 4 are mixed and combusted under the action of the full annular combustor 8. The high-temperature gas decelerates and expands through the outlet cap 10 at the rear end of the full annular combustor 8 and enters the outlet pipe section 5, and is stably discharged by the exhaust pipe section 6; during the whole combustion process, various performance indicators of the full annular combustor 8 are tested through measuring devices.
Claims
1. A full annular combustion chamber test device, characterized in that: It includes a guide pipe section, a drainage pipe section, an inlet pipe section, a test pipe section, an outlet pipe section and an exhaust pipe section which are connected in sequence. The guide pipe section cooperates with the air supply device. The guide pipe section is circumferentially provided with an annular drainage channel connected with the interior thereof. The inlet pipe section and the outlet pipe section are both provided with measuring devices for measuring test parameters. The test pipe section has a full annular combustion chamber built in. The rear port of the inlet pipe section is provided with an inlet cap cover for facilitating airflow acceleration and pressurization. The front port of the outlet pipe section is provided with an outlet cap cover for facilitating airflow deceleration and expansion.
2. The full annular combustion chamber test device according to claim 1, characterized in that: The inlet pipe section and the outlet pipe section are both tapered pipes, the large diameter end and the small diameter end of the inlet pipe section are smoothly connected to the drainage pipe section and the test pipe section respectively, and the small diameter end and the large diameter end of the outlet pipe section are smoothly connected to the test pipe section and the exhaust pipe section respectively.
3. The full annular combustion chamber test device according to claim 2, characterized in that: The inlet cap and the outlet cap are fixedly connected to the inner circumferential wall of the inlet pipe section and the outlet pipe section respectively through a plurality of support columns. The inlet cap and the outlet cap are both conical, and the cone tips of the inlet cap and the outlet cap point to the large diameter ends of the inlet pipe section and the outlet pipe section respectively.
4. The full annular combustion chamber test device according to claim 3, characterized in that: The inlet pipe section is provided with a fuel main pipe, the support column connected to the inlet cap is hollow inside, the fuel main pipe is led into the inlet cap through the inner cavity of the support column and is connected to a plurality of fuel small pipes in the full annular combustion chamber through a fuel adapter plate.
5. The full annular combustion chamber test device according to claim 1, characterized in that: The measuring device comprises a flue gas analyzer, a carbon emission detector and a plurality of total temperature and total pressure sensors, and the plurality of total temperature and total pressure sensors are evenly arranged in the circumferential direction at the front ports of the inlet pipe section and the outlet pipe section.
6. The full annular combustion chamber test device according to claim 1, characterized in that: The angle between the airflow direction of the annular drainage channel and the airflow direction inside the drainage pipe section is an acute angle.
7. The full annular combustion chamber test device according to claim 1, characterized in that: A rectifying honeycomb plate is arranged in the drainage pipe section, and the rectifying honeycomb plate is located at the rear end of the annular drainage channel.
8. The full annular combustion chamber test device according to claim 1, characterized in that: The air supply device is a micro turbojet engine, and a certain distance is maintained between the exhaust port of the micro turbojet engine and the front end port of the guide pipe section.
9. The full annular combustion chamber test device according to claim 1, characterized in that: An explosion-proof and high-temperature-resistant transparent window is arranged on the side wall of the test pipe section.